1) Blade tip stall is corrected by Report

Decreasing rotor speed

Unloading the rotor sytem

Increasing forward speed

2) Dissymmetry of lift in two-bladed rotors is often countered by using Report

See-saw systems

Lead-lag hinges

Offset hinges

3) Linking the cyclic control to a horizontal stabiliser enables Report

Better control of attitude

Increased airspeed

Better stall characteristics

4) To provide directional control, tail rotor systems must be capable of varying Report

Both negative and positive blade pitch

Lead-lag of individual blades

Direction of rotation

5) The main purpose of helicopter trim systems is to Report

Reduce the force required to operate flight controls

Match engine power to the position of the cyclic control

Maintain the correct attitude under different load conditions

6) Separation between collective and cyclic inputs to the swashplate is usually maintained by Report

A mixer

Torque tubes

A gradient unit

7) Aircraft structures must be designed to withstand specified ultimate loads Report

For a minimum of 3 seconds without failure

Without deformation at any time

That exceed the elastic limits of the materials used

8) The structural requirements for a "large aircraft" are contained in Report

JAR 23

JAR 25

JAR 27

9) Fixed surfaces of an aircraft, include Report

Ailerons, rudder and control tabs

Wings,horizontal stabilizer and vertical stabilizer

Wings, elevators and ailerons

10) Aircraft structures whose inherent strength greatly exceeds the design safety requirements may be classified as Report

Primary structures

Secondary structures

Fail safe structures

11) Aircraft seat rails are normally classified as Report

Primary structures

Secondary structures

Damage-tolerant structures

12) "Fail safe construction" is a method of aircraft design that enables Report

High-stress aerobatic aircraft manoeuvres

Longer periods between maintenance

Loads to be transferred to other components if a part of the structure fails

13) Aircraft may be allowed to continue flying with some structural damage provided that the damage is restricted to Report

Primary structures

Safe structures

Fail safe structures

14) The purpose of bonding straps fitted to bulkheads is to Report

Secure the bulkhead in position whilst allowing some movement.

Secure electrical cables and connectors to the bulkhead

Ensure a common electrical potential between the bulkhead and its securing points

15) Static electricity built up during flight is discharged on landing by Report

Static dischargers (static wicks)

Conductive tyres

Bonding straps

16) Static electricity built up during flight is discharged on landing by Report

Static dischargers (static wicks)

Conductive tyres

Bonding straps

17) Electrical resistance between aircraft structures is typically Report

Less than 0.5 ohms

Greater than 500 megohms

500 ohms

18) When refuelling aircraft, precautions must be taken to avoid Report

Getting rain into the fuel

Tilting due to uneven fuel flow

Build up of static electricity

19) Bonding tests on fuel systems must be carried out with Report

The components disconnected

A special Safety Ohmmeter

All fuel removed from the tanks

20) Damage to non-conductive aircraft components due to lightning strikes is minimised by fitting them with Report

Static dischargers

Conductive strips

Bonding straps

EASA Questions Module 13 Set 8

Set 1

Set 2

Set 3

Set 4

Set 5

Set 6

Set 7

Set 8

Set 9

Set 10

Set 11

Set 12